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S2027 (s2027-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S2027 (s2027-il)
Reynolds number: 200,000
Max Cl/Cd: 70.07 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2027-il-200000-n5.txt
Download as CSV file: xf-s2027-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2027                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5208   0.08258   0.07884  -0.0470   1.0000   0.0166
 -12.000  -0.5495   0.07217   0.06834  -0.0545   1.0000   0.0164
 -11.750  -0.5705   0.06464   0.06069  -0.0604   1.0000   0.0163
 -11.500  -0.5931   0.05794   0.05384  -0.0656   1.0000   0.0162
 -11.250  -0.6114   0.05282   0.04855  -0.0690   1.0000   0.0162
 -11.000  -0.6282   0.04862   0.04418  -0.0710   1.0000   0.0161
 -10.750  -0.6430   0.04532   0.04071  -0.0715   1.0000   0.0161
 -10.500  -0.6598   0.04279   0.03802  -0.0699   1.0000   0.0161
 -10.250  -0.6609   0.03974   0.03466  -0.0704   0.9804   0.0162
 -10.000  -0.6479   0.03654   0.03104  -0.0724   0.9630   0.0163
  -9.750  -0.6322   0.03396   0.02807  -0.0733   0.9487   0.0164
  -9.500  -0.6160   0.03189   0.02563  -0.0733   0.9353   0.0166
  -9.250  -0.5997   0.02969   0.02321  -0.0729   0.9234   0.0169
  -8.750  -0.5641   0.02668   0.01987  -0.0713   0.9010   0.0174
  -8.500  -0.5455   0.02548   0.01853  -0.0703   0.8905   0.0177
  -8.250  -0.5261   0.02449   0.01741  -0.0693   0.8811   0.0183
  -8.000  -0.5059   0.02363   0.01640  -0.0684   0.8710   0.0191
  -7.750  -0.4850   0.02273   0.01537  -0.0675   0.8618   0.0198
  -7.500  -0.4641   0.02180   0.01429  -0.0665   0.8532   0.0204
  -7.250  -0.4426   0.02090   0.01328  -0.0656   0.8436   0.0207
  -7.000  -0.4210   0.02008   0.01233  -0.0647   0.8355   0.0211
  -6.750  -0.3990   0.01931   0.01146  -0.0638   0.8264   0.0215
  -6.500  -0.3783   0.01841   0.01048  -0.0629   0.8178   0.0222
  -6.250  -0.3562   0.01772   0.00972  -0.0622   0.8094   0.0229
  -6.000  -0.3329   0.01713   0.00905  -0.0616   0.8008   0.0239
  -5.750  -0.3092   0.01661   0.00841  -0.0609   0.7928   0.0251
  -5.500  -0.2846   0.01615   0.00784  -0.0605   0.7840   0.0268
  -5.250  -0.2603   0.01566   0.00726  -0.0599   0.7763   0.0294
  -5.000  -0.2352   0.01522   0.00677  -0.0595   0.7674   0.0336
  -4.750  -0.2103   0.01474   0.00625  -0.0590   0.7595   0.0416
  -4.500  -0.1857   0.01417   0.00576  -0.0587   0.7509   0.0681
  -4.250  -0.1614   0.01359   0.00536  -0.0583   0.7429   0.1149
  -4.000  -0.1369   0.01304   0.00501  -0.0580   0.7345   0.1721
  -3.750  -0.1133   0.01237   0.00471  -0.0577   0.7264   0.2611
  -3.500  -0.0889   0.01189   0.00448  -0.0574   0.7182   0.3389
  -3.250  -0.0641   0.01150   0.00436  -0.0570   0.7098   0.4149
  -3.000  -0.0387   0.01128   0.00428  -0.0565   0.7021   0.4758
  -2.750  -0.0121   0.01118   0.00422  -0.0562   0.6933   0.5145
  -2.500   0.0150   0.01113   0.00413  -0.0558   0.6858   0.5403
  -2.250   0.0423   0.01108   0.00408  -0.0556   0.6769   0.5631
  -2.000   0.0696   0.01106   0.00401  -0.0554   0.6692   0.5838
  -1.750   0.0970   0.01105   0.00395  -0.0552   0.6606   0.6022
  -1.500   0.1245   0.01105   0.00389  -0.0550   0.6527   0.6183
  -1.250   0.1519   0.01105   0.00385  -0.0548   0.6445   0.6331
  -1.000   0.1794   0.01105   0.00381  -0.0546   0.6363   0.6468
  -0.750   0.2068   0.01106   0.00377  -0.0544   0.6284   0.6599
  -0.500   0.2342   0.01107   0.00375  -0.0542   0.6201   0.6723
  -0.250   0.2617   0.01110   0.00372  -0.0541   0.6124   0.6846
   0.000   0.2892   0.01112   0.00373  -0.0539   0.6039   0.6968
   0.250   0.3163   0.01115   0.00371  -0.0537   0.5965   0.7082
   0.500   0.3435   0.01117   0.00374  -0.0535   0.5879   0.7198
   0.750   0.3706   0.01122   0.00375  -0.0533   0.5803   0.7316
   1.000   0.3977   0.01125   0.00379  -0.0531   0.5719   0.7440
   1.250   0.4245   0.01130   0.00382  -0.0528   0.5642   0.7564
   1.500   0.4511   0.01134   0.00388  -0.0525   0.5560   0.7689
   1.750   0.4776   0.01139   0.00394  -0.0522   0.5482   0.7821
   2.000   0.5039   0.01145   0.00401  -0.0518   0.5402   0.7959
   2.250   0.5300   0.01151   0.00408  -0.0514   0.5323   0.8105
   2.500   0.5558   0.01157   0.00417  -0.0509   0.5243   0.8261
   2.750   0.5815   0.01164   0.00426  -0.0504   0.5165   0.8430
   3.000   0.6072   0.01172   0.00435  -0.0499   0.5086   0.8617
   3.250   0.6332   0.01179   0.00447  -0.0495   0.5004   0.8823
   3.500   0.6604   0.01188   0.00456  -0.0493   0.4926   0.9053
   3.750   0.6913   0.01197   0.00470  -0.0499   0.4838   0.9302
   4.000   0.7262   0.01210   0.00482  -0.0515   0.4755   0.9567
   4.250   0.7637   0.01223   0.00496  -0.0537   0.4659   0.9866
   4.500   0.7926   0.01241   0.00512  -0.0543   0.4576   1.0000
   4.750   0.8174   0.01261   0.00530  -0.0539   0.4493   1.0000
   5.000   0.8425   0.01281   0.00549  -0.0536   0.4408   1.0000
   5.250   0.8673   0.01304   0.00568  -0.0533   0.4328   1.0000
   5.500   0.8925   0.01324   0.00591  -0.0530   0.4238   1.0000
   5.750   0.9172   0.01349   0.00615  -0.0526   0.4157   1.0000
   6.000   0.9418   0.01373   0.00640  -0.0523   0.4067   1.0000
   6.250   0.9663   0.01399   0.00666  -0.0519   0.3981   1.0000
   6.500   0.9903   0.01426   0.00694  -0.0514   0.3895   1.0000
   6.750   1.0144   0.01454   0.00726  -0.0510   0.3805   1.0000
   7.000   1.0378   0.01485   0.00756  -0.0505   0.3720   1.0000
   7.250   1.0611   0.01515   0.00790  -0.0499   0.3625   1.0000
   7.500   1.0840   0.01547   0.00825  -0.0494   0.3537   1.0000
   7.750   1.1061   0.01583   0.00863  -0.0486   0.3448   1.0000
   8.000   1.1284   0.01617   0.00903  -0.0480   0.3354   1.0000
   8.250   1.1495   0.01656   0.00944  -0.0471   0.3265   1.0000
   8.500   1.1696   0.01697   0.00987  -0.0462   0.3161   1.0000
   8.750   1.1890   0.01739   0.01034  -0.0451   0.3045   1.0000
   9.000   1.2068   0.01785   0.01082  -0.0438   0.2925   1.0000
   9.250   1.2233   0.01836   0.01134  -0.0424   0.2805   1.0000
   9.500   1.2374   0.01890   0.01189  -0.0406   0.2676   1.0000
   9.750   1.2486   0.01950   0.01249  -0.0384   0.2553   1.0000
  10.000   1.2596   0.02016   0.01318  -0.0363   0.2431   1.0000
  10.250   1.2712   0.02086   0.01392  -0.0344   0.2314   1.0000
  10.500   1.2817   0.02165   0.01474  -0.0326   0.2199   1.0000
  10.750   1.2898   0.02260   0.01570  -0.0306   0.2062   1.0000
  11.000   1.2956   0.02374   0.01682  -0.0287   0.1905   1.0000
  11.250   1.2983   0.02516   0.01818  -0.0267   0.1730   1.0000
  11.500   1.2998   0.02677   0.01973  -0.0248   0.1537   1.0000
  11.750   1.2983   0.02871   0.02159  -0.0231   0.1338   1.0000
  12.000   1.2958   0.03087   0.02366  -0.0216   0.1152   1.0000
  12.250   1.2953   0.03302   0.02580  -0.0204   0.1010   1.0000
  12.500   1.2944   0.03531   0.02807  -0.0194   0.0890   1.0000
  12.750   1.2924   0.03781   0.03057  -0.0186   0.0781   1.0000
  13.250   1.2891   0.04304   0.03586  -0.0176   0.0618   1.0000
  13.500   1.2861   0.04595   0.03880  -0.0174   0.0548   1.0000
  13.750   1.2816   0.04914   0.04202  -0.0173   0.0483   1.0000
  14.000   1.2801   0.05215   0.04511  -0.0175   0.0435   1.0000
  14.500   1.2724   0.05904   0.05212  -0.0183   0.0349   1.0000
  14.750   1.2663   0.06297   0.05610  -0.0190   0.0311   1.0000
  15.000   1.2622   0.06674   0.05998  -0.0199   0.0283   1.0000
  15.250   1.2576   0.07071   0.06404  -0.0209   0.0258   1.0000
  15.500   1.2502   0.07519   0.06861  -0.0222   0.0239   1.0000
  15.750   1.2446   0.07951   0.07305  -0.0235   0.0223   1.0000
  16.000   1.2390   0.08396   0.07762  -0.0249   0.0207   1.0000
  16.250   1.2326   0.08863   0.08240  -0.0266   0.0195   1.0000
  16.500   1.2240   0.09375   0.08760  -0.0285   0.0184   1.0000
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